CN101131094A

CN101131094A - Tip ramp turbine blade

Info

Publication number: CN101131094A
Application number: CNA2007101417248A
Authority: CN
Inventors: K·S·克拉辛; 李经邦; P·H·维特; B·D·凯思
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2006-08-21
Filing date: 2007-08-21
Publication date: 2008-02-27
Also published as: JP2008051094A; CN104594955A; EP1903183A2; CA2597654A1; CA2597654C; CN104594955B; US8512003B2; EP1903183B1; US20080044289A1; JP5306613B2; EP1903183A3

Abstract

A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.

Description

Tip ramp turbine blade

Technical field

Relate generally to gas turbine engine of the present invention, and more specifically relate to its interior turbine bucket.

Background technique

In gas turbine engine, air in compressor pressurized and in burner with fuel mix to generate combustion gas.Multiple turbine stage obtains energy to drive motor and to produce merit from combustion gas.

High pressure turbine (HPT) is directly followed burner and is obtained energy to drive the upstream compressor by a live axle from the hottest combustion gas.Low-pressure turbine (LPT) is followed HPT and is obtained other energy to drive another live axle from combustion gas.In the turbofan aeroengine was used, LPT drove upstream fan, or drove external shaft in sea-freight and commercial Application.

Engine efficiency and specific fuel consumption (SFC) are very important purpose of design in modern gas turbine engines.Multiple turbine rotor blade and respective nozzles stator thereof have accurately the aerodynamic surface of structure, to control speed on it and pressure distribution with the maximization aerodynamic efficiency.

The respective airfoil of blade and stator have axially extend in tangential between relative leading edge and trailing edge usually recessed on the pressure side and the suction side of usually protruding.Fin has crescent profile on radial cross section, this profile genesis width in the past rapidly increases to the Extreme breadth zone, and width little by little is reduced to trailing edge then.

Circumferential or the horizontal relative side of fin is also radially extended in the span from the root to the tip.Fin typically has the thin sidewall that is formed by the superalloy metal casting, has internal cooling circuit, and internal cooling circuit has various embodiments, and these embodiments customize especially to cool off fin effectively at run duration and make maximizing efficiency simultaneously.

Yet the aerodynamic design of turbine airfoil is complicated significantly because the three-dimensional (3D) of the independent fin in the complete line of fin is constructed, and has guided the gas flow of corresponding complexity between fin at run duration.Except that this design and environmental complexity, around the radially outer tip of turbine bucket, have special flow field, this turbine bucket is high speed rotating in the static cover that run duration is centering on.

Operation slit between vane tip and turbine shroud or gap should be as far as possible little of to minimize the leakage of gas flow by it according to reality, and the while also allows the thermal expansion and the contraction of blade and cover, and does not have undesirable friction between the most advanced and sophisticated and static cover of rotation.

At run duration, the vane drive supporting rotor disc spins of turbo machine in capable, make the fin suction side relative fin on the pressure side before.Fin typically twists from the heel to the tip in radial direction from the periphery of rotor disk, and leading edge and engine shaft are to the cener line sloping floor upstream, with the discharging cyclone angle of the inclination of the nozzle guide vane of coupling cooperation.Combustion gas is usually flowed in the axial downstream direction, make circumferentially or tangential component at first a flow direction engagement tabs leading edge, and on the trailing edge of fin, leave fin then with different flow directions.

Fin on the pressure side have corresponding different 3D profile with suction side, with maximization therebetween differential pressure and the energy that from hot combustion gas, obtains.Recessed has on the pressure side realized speed different on it and pressure distribution with the suction side of protruding, and this correspondingly changes between leading edge and trailing edge and from the heel to the tip.Yet, produced very little useful work if above the fin tip, have in the combustion gas of the most advanced and sophisticated slit internal leakage that requires.

Further make turbine bucket design complicated be the vane tip that exposes, therefore this tip is immersed in the combustion gas that leak the side in service from it, and requires the suitable cooling at tip to guarantee the working life of turbine bucket in the length of run duration.

Modern turbine bucket design has typically merged the most advanced and sophisticated rib of singing (squealer), the most advanced and sophisticated rib of singing be fin on the pressure side with the little radially extension from the leading edge to the trailing edge of suction side.Most advanced and sophisticated rib typically has the rectangular cross-section and laterally or circumferentially separately being limited to the most advanced and sophisticated chamber of opening on the fin top, and this chamber, tip has the bottom, integrated type tip of the internal cooling circuit of having sealed typical hollow fin and Qi Nei.

Little most advanced and sophisticated rib provides expendable material under most advanced and sophisticated friction situation, prevent from undesirably to damage to protect most advanced and sophisticated bottom and internal cooling circuit.Most advanced and sophisticated rib has increased the complexity of gas flow field, thereby has introduced local secondary field, and this secondary field influences turbine efficiency, flows and leak and most advanced and sophisticated cooling.

The main flow direction of combustion gas is the axial downstream direction in the runner that is limited between the blade of vicinity.Axial flow also radially changes to the tip from the heel of each fin.And these axially and the Radial Flow variation above the fin tip, be compound further, combustion gas on the pressure side and between the suction side leaking herein at each fin.

Therefore, prior art is full of the turbine blade tip structure that multiple solution comprises that turbine efficiency, the most advanced and sophisticated and most advanced and sophisticated different problems of cooling off and performance of leaking are considered.These three important considerations are complementary at least on part, but cause its quite complicated assessment at the fin bit point and in the 3D flow field of different pressures side between leading edge and the trailing edge and the complexity above the suction side.

Yet modern computing hydrokinetics (CFD) comprises powerful software, and software has improved the stream mathematical analysis's capability that the complicated 3D in the gas turbine engine is flowed and the further improved mechanism that can realize the turbine bucket design with it is provided.

For example, wish to leak, or increase turbine efficiency, or improve most advanced and sophisticated cooling by reducing most advanced and sophisticated flowing, or any combination that separate or together of these factors and improve the turbine blade tip design.

Summary of the invention

Turbine bucket comprises the first and second most advanced and sophisticated ribs that extend from most advanced and sophisticated bottom, to limit most advanced and sophisticated chamber.Leave inclined-plane bridge joint rib and raise to tail height from the bottom.

Description of drawings

In following detailed description, according to preferred and typical embodiment, the present invention and further purpose and advantage have been described more specifically in conjunction with the accompanying drawings, each figure is:

Fig. 1 is the axonometric drawing such as grade that the part of typical turbine rotor blade is cut open;

Fig. 2 is the radial cross section view by illustrated turbine airfoil among Fig. 1 and 2-2 along the line;

Fig. 3 is the preceding axonometric drawing that waits at illustrated fin tip among Fig. 1;

Fig. 4 is the chordwise section view by the afterbody end at illustrated fin tip among Fig. 1 and 4-4 along the line;

Fig. 5 is the transverse sectional view by illustrated fin 5-5 most advanced and sophisticated and along the line among Fig. 3;

Fig. 6 be according to the embodiment who substitutes in Fig. 1 illustrated fin tip wait axonometric drawing;

Fig. 7 be according to the embodiment who substitutes in Fig. 1 illustrated fin tip wait axonometric drawing;

Fig. 8 be according to the embodiment who substitutes in Fig. 1 illustrated fin tip wait axonometric drawing.

Embodiment

Fig. 1 illustrates the typical first order turbine rotor blade 10 that uses in the HPT of gas turbine engine.Typically the blade by the superalloy metal casting have fin 12, at the platform 14 at its heel place and the supporting dovetail joint 16 of unitary one-piece assembly.

Dovetail joint 16 can have any conventionally form, the illustrated dovetail joint that axially enters in Fig. 1 for example, and it is with in the corresponding dovetail tongue-and-groove of blade installation in the periphery of supporting rotor dish (not shown).Dish has kept the full line blade that circumferentially separates mutually, to limit vane channel between it.

At run duration, combustion gas 18 generates in the (not shown) of the firing chamber of motor and is directed to the downstream suitably on corresponding turbine bucket 10, and blade 10 obtains energy to drive the supporting rotor dish from combustion gas.Independent platform 14 provides the inner radial border of combustion gas and has adjoined the platform of the vicinity in the complete line of turbine bucket.

Illustrated fin 12 comprises circumferentially or laterally relative on the pressure side 20 and suction side 22 among Fig. 1 and Fig. 2, extend axially in their tangential between relative leading edge 24 and trailing edge 26, and in the span of fin heel 28, radially extending to terminate in radially outer tip cap or most advanced and sophisticated 30.Fin on the pressure side 20 usually is being recessed between leading edge and the trailing edge and and fin suction side 22 complementations of protrusion usually between leading edge and trailing edge.

Fin on the pressure side 20 and the outer surface of suction side 22 have typical crescent shape or profile, conventional being configured to realizes that at run duration combustion gas corresponding speed and pressure distribution thereon obtains with the energy of maximization from combustion gas.

Fig. 2 illustrates the exemplary radial cross section and the typical crescent profile thereof of fin, and desired as obtaining energy from combustion gas, it changes to the tip from the root of fin suitably.Various radial cross sections are common, and to be fin increase sharply in the raised position from the Extreme breadth of leading edge 24 before afterbody is to the string at fin just on the horizontal width, make fin then width be reduced to narrow or thin trailing edge 26 gradually.

Fin 12 hollow typically and comprise internal cooling circuit 32, cooling circuit 32 can have the structure of any routine, for example illustrated two terminate in after the leading edge and trailing edge before corresponding runner in the threeway loop of wriggling.Cooling circuit extends through platform and dovetail joint, has corresponding inlet at the dovetail joint base portion, is used for receiving in the mode of any routine from the compressor (not shown) of motor the cooling air 34 of pressurization.

In this way, blade pass cross inner cooling air from heel to most advanced and sophisticated and leading edge and trailing edge by inner cooling, cooling air can be by thin fin sidewall with multiple row discharging with film cooling hole of stock size and structure then.

Because the fin leading edge typically is subjected to the hottest incoming flow combustion gas, the special cooling of fin leading edge provides in any suitable manner.And the thin trailing edge zone of fin typically comprises the row of the slit of trailing edge cooling on the pressure side, to discharge the part of the cooling air of using.

As mentioned above, the turbine airfoil 12 that illustrates at first in Fig. 1 has accurately the 3D profile of structure, and this 3D profile has correspondingly influenced combustion gas 18 when in speed and the pressure distribution of axial downstream direction when leading edge 24 flows to trailing edge 26.Blade attachment is to the periphery of supporting disk and in the run duration rotation, this has generated secondary flow field in combustion gas, makes combustion gas along the typically radially outward migration of fin span.

In addition, the relative pressure of the combustion gas on 20 on the pressure side at fin is higher than along the pressure of fin suction side, and run duration when its radially to the upper reaches and to flow through the fin of exposure most advanced and sophisticated 30 the time, it has introduced further secondary or three grades of influences with the corresponding rotation of run duration blade in gas flow field.

Above-described turbine rotor blade can be conventional in structure and operation, uses in gas turbine engine, comprises and for example using in the first order of HPT.Conventional blade can be revised at most advanced and sophisticated 30 places of fin then as hereinafter, to comprise most advanced and sophisticated rib 36 of first singing and the most advanced and sophisticated rib 38 of second singing, they be respectively fin on the pressure side or the extension of sidewall 20 and suction side or sidewall 22 integral body diametrically, and on profile or curvature, conform to it.

First rib or pressure side rib 36 meet recessed on the pressure side 20 the shape or the profile of fin on tangential, and correspondingly second rib or suction side rib 38 meet the suction side 22 of the protrusion of fin on tangential profile.

As extending radially outwardly from common most advanced and sophisticated bottom 40 at two

ribs

36,38 shown in Fig. 1 and Fig. 3, most advanced and sophisticated bottom lock internal cooling circuit 32.Most advanced and sophisticated bottom 40 can be for atresia, perhaps can comprise little cooling hole or bigger dirt hole, with will be with the cooling air of crossing from the inner discharge of fin.

Two

ribs

36,38 between axial or tangential relative leading edge 24 and trailing edge 26 along fin accordingly on the pressure side 20 and suction side 22 extend continuously, to limit and to be provided for the complete perimeter border in most advanced and sophisticated depression or chamber 42.Most advanced and sophisticated chamber radially outward is faced, and has opening mouth or inlet, itself and the most advanced and sophisticated rib that centers on 36,38 coplanes that preferably have height common and constant on the most advanced and sophisticated bottom.

Schematically illustrated run duration in as Fig. 3, combustion gas 18 separates along fin leading edge 24, and along fin relative on the pressure side with the suction side flow further downstream.Some radially outwards of these combustion gas move, and flow through the fin tip, and enter open pointed tip chamber 42.In inboard, open pointed tip chamber, combustion gas development secondary or three grades of flow fields and eddy current, and flow towards trailing edge 26 to afterbody.

Therefore, revise the fin tip especially to comprise discharging or to leave inclined-plane 44 that it is the horizontal relative most advanced and

sophisticated rib

36,38 of bridge joint near thin trailing edge 26.Leaving the inclined-plane increases or rising towards the trailing edge height to afterbody from its afterbody end junction point with most advanced and sophisticated bottom 40.

Leave inclined-plane 44 in Fig. 4 with vertical profile diagram along the tangential axis of fin, in Fig. 5, stride across relative on the pressure side and the width of the fin between the suction side illustrate with viewgraph of cross-section.Leave the inclined-plane and comprise forward the anterior area 46 of extending towards leading edge 24, its smoothly and the afterbody end of the most advanced and sophisticated bottom 40 between two

ribs

36,38 merge.The inclined-plane also comprises to afterbody towards afterbody area 48 that trailing edge 26 extends and merges smoothly with the outside or the top surface at fin tip.

Differently construct in two

areas

46,48, with differently with the relative partial fusion in most advanced and sophisticated chamber, make that the higher afterbody area 48 of anterior regional 46 aspect ratios is low.Leaving inclined-plane 44 preferably also comprises from anterior regional 46 to the outward-dipping or tilting intermediate area 50 to higher afterbody area 48 of afterbody.

Fig. 3-5 illustrates fin recessed on the pressure side 20 and the suction side 22 protruded be focused at together towards trailing edge 26 to afterbody.And most advanced and

sophisticated rib

36,38 is focused at together to afterbody similarly, because they become whole with the outer end of fin side.

Most advanced and sophisticated chamber 42 is defined by two

ribs

36,38 fully, and self assembles towards fin trailing edge width to afterbody.Two

ribs

36,38 are shared anterior rib junction point at leading edge 24 places, disperse on horizontal spacing and converge to another junction point at the trailing edge place to afterbody then.

Especially, fin trailing edge 26 relative thin, and two

thin ribs

36,38 at common afterbody rib junction point 52 places just the trailing edge upstream parallel in conjunction with or merge.Initial each than two

ribs

36,38 of rib junction point is wide, and typically converges to afterbody with common rib part in conventional practice and approach trailing edge 26.

Therefore, leave inclined-plane 44 and introduce at the afterbody end place in most advanced and sophisticated chamber 42, wherein it converges to its minimum width at afterbody rib junction point 52 places.Leaving the inclined-plane provides from most advanced and sophisticated bottom 40 the aerodynamic of rib junction point 52 to high height of lower height and seamlessly transits, the height place and two ribs, 36,38 shared common radially outer outer surfaces of its common or coplane on most advanced and sophisticated bottom 40.

Fig. 5 illustrates around the part of the turbine shroud 54 of the capable routine of whole turbine rotor blades, to provide relatively little radial gap or gap between the radially outer outer surface at internal surface that covers and fin tip.At run duration, the part of combustion gas 18 is laterally on the pressure side leaked to relative fin suction side from fin by most advanced and sophisticated slit.

Introduce that the illustrated inclined-plane 44 that leaves provides the aerodynamics of the combustion gas of meeting from fin most advanced and sophisticated chamber 42 dischargings with the combustion gas of leaking in the trailing edge zone of fin to seamlessly transit among Fig. 3-5.

Fig. 4 illustrates preferred profile or the profile that leaves inclined-plane 44 at the tangential of fin or axially, is used to provide the aerodynamics of combustion gas to seamlessly transit.When combustion gas during from the discharging of the afterbody end in most advanced and sophisticated chamber, wish to reduce or the flow point of eliminating combustion gas from, and correspondingly reduce the relative pressure loss.

As shown in the figure, inclined-plane 44 is vertical or tangentially have a total length L at it, and it is preferably more than the respective depth D in the most advanced and sophisticated chamber 42 that begins to locate of self on the inclined-plane.

Inclined-plane 44 tilts or raises to afterbody with the tilt angle of acute angle or angle of tilt A, and it is preferably fully shallow, with minimize along the flow point of its combustion gas of flowing from.The tilt angle, inclined-plane can for about 15 spend about 60 the degree, depend on influence flow point from flow performance.

As shown in Figure 5, inclined-plane 44 forwardly reduces on width W or assembles to afterbody between area 46 and the afterbody area 48, and the while inclined-plane is highly increase between it.

In this structure, directly reduce at the afterbody part flow further downstream area on the inclined-plane that leaves the most advanced and sophisticated chamber on the inclined-plane 44, therefore quickened the combustion gas of flowing along it.This local flow quickens to have increased the speed and the momentum of combustion gas, to improve the aerodynamic performance of turbine bucket.

Fig. 4 illustrate anterior area 46 and afterbody area 48 how on the inclined-plane vertically or downstream direction differently merge respectively with most advanced and sophisticated bottom 40 and rib junction point 52.Anterior area 46 preferably tangential recessed and to the outside to, to merge smoothly with relative flat most advanced and sophisticated bottom 40.Correspondingly, preferably outwards protrude in afterbody area 48, wherein, and itself and the outer surface fusion of rib junction point 52.

As shown in Figure 5, leaving inclined-plane 44 is straight along its horizontal width between two

relative ribs

36,38 preferably, and is attached to rib with relatively little arc fillet.The width W of leaving the inclined-plane should not reduce or eliminate the suitable minimum value of about 30mil (7.6mm) of its benefit less than meeting.If most advanced and sophisticated chamber or to leave the inclined-plane too narrow, so narrow part in chamber is flow through in the combustion gas meeting of leaking on the fin tip in narrow zone simply, also has only very little aerodynamic performance to improve if having.

As mentioned above, the total length L of leaving the inclined-plane is preferably more than the depth D in most advanced and sophisticated chamber, and can be about three times of this degree of depth, to have suitable transition gradually combustion gas is guided out the chamber smoothly.Intermediate area 50 is preferably tangential is longer than anterior area 46, and merges smoothly and together with it with prolonging.Intermediate area 50 is also preferably long than afterbody area 48, and also merges smoothly and together with it with prolonging.

Like this, anterior area 46 and afterbody area 48 can be provided in the base portion that leaves the inclined-plane and the corresponding different transition at place, top, make intermediate area 50 be provided at transition long on the degree of depth of corresponding most most advanced and sophisticated chamber.

Because anterior area 46 is preferably recessed, and afterbody area 48 preferably protrudes, and intermediate area 50 can have any suitable and preferred different profile betwixt, with the enhancing aerodynamic performance.For example, intermediate area 50 is forwardly tangential straight between area and the afterbody area, with effectively from the discharging combustion gas of most advanced and sophisticated chamber.

In Fig. 1,3,5 among the illustrated typical embodiment, two most advanced and

sophisticated ribs

36,38 define fully fin on the pressure side and suction side, to limit single most advanced and sophisticated chamber 42, it converges to the single inclined-plane 44 that leaves to afterbody.Like this, some of most advanced and sophisticated gas leakage flow through second rib 38 near leading edge 24, and enter most advanced and sophisticated chamber 42, to flow towards leaving inclined-plane 44 to afterbody.The inclined-plane that leaves that defines as the afterbody end by two

ribs

36,38 quickens then from the gas of most advanced and sophisticated chamber discharging.Less pressure is in the internal loss of most advanced and sophisticated chamber, and it correspondingly increases cavity pressure, and reduces the leakage on the fin tip again.

Leaving inclined-plane 44 can be introduced in conjunction with other features such as the arc expansion portion 56 of extending along the roughly whole length of first rib 36 among Fig. 1-5 in the illustrated turbine rotor blade.Expansion portion 56 from fin on the pressure side 20 radially outwards disperse, to increase to the resistance of combustion gas by tip-cover Gap Flow.

Carried out the CFD analysis for the illustrated typical fin tip in Fig. 1-5 that has and do not have expansion portion 56, and with respect to the reference fin tip of leaving inclined-plane or expansion portion of the performance that does not influence other conventional first and second most advanced and

sophisticated ribs

36,38.

In the embodiment of expansion portion not, the gas leakage on the fin tip can leave the inclined-plane and significantly reduces by introducing, and also can obtain the remarkable improvement of turbine efficiency.

For for example being included in the illustrated embodiment who leaves the combination of inclined-plane 44 and on the pressure side most advanced and sophisticated expansion portion 56 in Fig. 3 and 5, not observing detectable most advanced and sophisticated the leakage and change.Yet introducing expansion portion has further increased the turbine efficiency of being left the independent acquisition in inclined-plane by use.

Owing to leave the relative simplicity on inclined-plane 44, it can be used for having various other embodiments of the turbine rotor blade in one or more most advanced and sophisticated chamber.

For example, Fig. 6 illustrates the pointed tip configuration that substitutes that is used for the illustrated turbine bucket of Fig. 1, not expansion portion 56.In this structure, one or more tip baffle 58 is horizontal two ribs of bridge joint 36,38 before leaving inclined-plane 44.In Fig. 6, two of tip baffle 58 provide and tangential separating for limiting three most advanced and sophisticated chambeies or cave, the opposite side of bridge joint fin.

The inclined-plane 44 that leaves described above can be introduced the last or most advanced and sophisticated chamber of afterbody among Fig. 6 similarly, to discharge combustion gas to afterbody at rib junction point 52 from it smoothly.In this embodiment, the intermediate area that leaves the inclined-plane can protrude on tangential a little, to merge with the afterbody area of protruding.

Fig. 7 illustrates another embodiment again at the fin tip of band expansion portion, and wherein, heteroid tip baffle 60 is near the tangential afterbody part that extends to the identical second rib 38 before the trailing edge 26 of the anterior part of the second rib 38 the leading edge 24.Tangential baffle plate 60 bifurcated fin tip in the zone of the Extreme breadth at fin tip is first most advanced and sophisticated chambeies 42 of edge 20 extensions on the pressure side and the second most advanced and sophisticated chamber 42 of extending along suction side 22.

In this embodiment, each of two most advanced and sophisticated chambeies 42 can be included in place, its afterbody end leave inclined-plane 44 leave the inclined-plane accordingly.The afterbody end of tip baffle 60 and the intermediate portion of second rib 38 merge, so that the corresponding rib junction point as the rib junction point 52 between the afterbody end of two

ribs

36,38 to be provided.

Two most advanced and sophisticated chambeies 42 are assembled at downstream direction, and leave inclined-plane 44 accordingly and can introduce wherein, smoothly discharge with the aerodynamics that combustion gas each from two chambeies is provided, and are used for discharging on the appropriate section of suction side second rib 38.

Fig. 8 illustrates another embodiment again at the fin tip of not expansion portion, and wherein, different tip baffles 62 is near the intermediate portion of the tangential relative first rib 36 before afterbody extends to trailing edge 26 of anterior part of the second rib 38 the leading edge 24.Tangential tip baffle 60 bifurcated fins tip is along 20 the first most advanced and sophisticated chamber 42 on the pressure side with along the second most advanced and sophisticated chamber 42 of suction side 22.Each of two most advanced and sophisticated chambeies can be included in place, its afterbody end leave inclined-plane 44 leave the inclined-plane accordingly.

In Fig. 7, tip baffle 60 has relative with the protrusion profile of second rib 38 or opposite and the tangential profile relative with the recessed profile of first rib 36.In Fig. 8, tip baffle 62 has the tangential profile that protrusion profile with second rib 38 is similar or conform to and also conform to the recessed profile of first rib 36.

Among illustrated two embodiments, corresponding

tip baffle

60,62 horizontal bifurcated fin tips are two chambeies in Fig. 7 and 8, and it extends towards common trailing edge 26 in caudal directions.When fin converged to trailing edge, two chambeies in two embodiments were assembled.And the inclined-plane 44 that leaves of convergence can be introduced at the place, afterbody end in two chambeies of two embodiments, has in turbine efficiency and most advanced and sophisticated confers similar advantages in flowing leakage.

More than the different embodiment at the different fin tip of Pi Luing causes the different aerodynamic performance of turbine rotor blade.When combustion gas flow through downstream fin on the pressure side with suction side the time, the speed of combustion gas and pressure distribution will be according to different designs corresponding changes on the fin tip at fin tip.

Therefore, if require from most advanced and sophisticated chamber to leave accordingly when having also with little flow point from the discharging combustion gas on the inclined-plane when independent fin tip design, more than the specific structure that leaves inclined-plane 44 and the size of Pi Luing can change.Reducing will correspondingly increase pressure in the most advanced and sophisticated chamber by the pressure loss in the most advanced and sophisticated gas flow in most advanced and sophisticated chamber, and the tip that is used to reduce on the fin tip flows leakage.

To be accelerated to fair speed and higher momentum leaving the chamber stream that discharges on the inclined-plane, with for different designs with leave the different placements of inclined-plane in heteroid fin tip and come with the corresponding improvement turbine efficiency of different amounts.

Though described at this and to be considered to preferred and typical embodiment of the present invention; but it is obvious that other modifications of the present invention of teaching are from here tackled in the art technology those skilled in the art, and therefore hope subsidiary claims that are modified in that fall in true spirit of the present invention and the scope that all are such are protected.

Therefore, wish to be the present invention who in claims subsequently, limits and distinguished by the U. S. Patent protection.

Parts list

10 rotor blades

12 fins

14 platforms

16 supporting dovetails

18 combustion gas

20 on the pressure side

22 suction side

24 leading edges

26 trailing edges

28 fin heels

30 tips

32 cooling circuits

34 cooling airs

36 first most advanced and sophisticated ribs

38 second most advanced and sophisticated ribs

40 most advanced and sophisticated bottoms

42 most advanced and sophisticated chambeies

44 leave the inclined-plane

46 anterior areas

48 afterbody areas

50 intermediate areas

52 rib junction points

54 turbine shrouds

56 expansion portions

58 tip baffles

60 tip baffles

62 tip baffles

Claims

1. a turbine bucket (10), it comprises:

Fin (12), platform (14) and integrated type dovetail joint (16);

Described fin (12) be included between relative leading edge (24) and the trailing edge (26) tangential extension and in span from heel (28) to most advanced and sophisticated (30) horizontal relative on the pressure side (20) and the suction side (22) of longitudinal extension;

Described tip (30) is included between described leading edge (24) and the trailing edge (26) from most advanced and sophisticated bottom (40) along described on the pressure side (20) and suction side (22) the outward extending first most advanced and sophisticated rib (36) and the second most advanced and sophisticated rib (38), to limit most advanced and sophisticated chamber (42); With

Leave inclined-plane (44), near its its described first rib of afterbody junction point bridge joint (36) described trailing edge (26) and second rib (38) and raise to tail height from described most advanced and sophisticated bottom (40).

2. blade according to claim 1, wherein said on the pressure side (20) are recessed into and described suction side (22) is protruded, and are focused at together towards described trailing edge (26) to afterbody;

The described first most advanced and sophisticated rib (36) and the second most advanced and sophisticated rib (38) form wholely with described on the pressure side (20) and suction side (22) respectively, and define described most advanced and sophisticated chamber (42), with converge to tail width described rib junction point (52) and

Described inclined-plane (44) is assembled to tail width.

3. blade according to claim 2, wherein said inclined-plane (44) comprise forward the anterior area (46) of merging with described most advanced and sophisticated bottom (40), with described rib (36,38) the afterbody area (48) that described afterbody junction point (52) merges and be tilted out to the intermediate area (50) in described afterbody area (48) from described anterior area (46).

4. blade according to claim 3, the length of wherein said inclined-plane (44) is greater than the degree of depth in described most advanced and sophisticated chamber (42).

5. blade according to claim 3, wherein said inclined-plane (44) raise to afterbody with shallow tilt angle.

6. blade according to claim 3, differently merge with described most advanced and sophisticated bottom (40) and rib junction point (52) in wherein said anterior area (46) and afterbody area (48).

7. blade according to claim 3, the tangential recessed and tangential protrusion in described afterbody area (48) in wherein said anterior area (46).

8. blade according to claim 3, wherein said intermediate area (50) are longer than described anterior area (46) and are merged smoothly with it, and are longer than described afterbody area (48) and merge smoothly with it.

9. blade according to claim 3, wherein said intermediate area (50) is tangential to be straight.

10. blade according to claim 3, the wherein said first most advanced and sophisticated rib (36) and the second most advanced and sophisticated rib (38) define described on the pressure side (20) and suction side (22), converge to the single single most advanced and sophisticated chamber (42) of leaving inclined-plane (44) to limit to afterbody.